US20100237049A1

US20100237049A1 - Preheating temperature during remelting

Info

Publication number: US20100237049A1
Application number: US12/681,821
Authority: US
Inventors: Selim Mokadem
Original assignee: Siemens AG
Current assignee: Siemens AG
Priority date: 2007-10-08
Filing date: 2008-06-25
Publication date: 2010-09-23
Also published as: WO2009047024A1; EP2207642A1

Abstract

A method of welding a component is provided. The component is welded using a preheating temperature of the component below 500° C. and above 400° C., wherein no material is added to an area to be welded.

Description

CROSS REFERENCE TO RELATED APPLICATIONS

This application is the US National Stage of International Application No. PCT/EP2008/058058 filed Jun. 25, 2008, and claims the benefit thereof. The International. Application claims the benefits of European Patent Application No. 07019670.4 EP filed Oct. 8, 2007. All of the applications are incorporated by reference herein in their entirety.

FIELD OF INVENTION

The invention relates to a method of welding using a preheating temperature. Especially a Ni base, especially a single crystal (SX) superalloy substrate is repaired by using a laser beam while preheating the substrate to an optimized temperature.

BACKGROUND OF INVENTION

This is useful because blades are expensive, especially for single crystalline components (SX) components.
The U.S. Pat. No. 5,374,319 teaches that the preheating temperature during welding lies at 760° C., preferably at a higher temperature of 920° C.
After casting or after service high temperature turbine parts (e.g. turbine blades or vanes) may present surface cracks that must be repaired prior proceeding.

SUMMARY OF INVENTION

It is an object of the invention to overcome this problem.
The object is achieved by a method according to the independent claim. Further advantageous steps are listed in the dependent claims which can be combined arbitrarily which each other to yield further advantages.
A laser assisted process is foreseen for the repair of cracks affecting SX turbine parts by surface local controlled laser remelting.
When SX components are laser treated, two main types of defects might affect the repaired zone: spurious grains and solidification cracking.
The conditions for successful SX repair on SX components require epitaxial and columnar growth and avoiding equiaxed or misoriented columnar growth responsible for grain boundaries formation. To guarantee a SX structure, a precise process control that insures epitaxial columnar growth is essential.
Apart from the microstructure control, conditions which produce crack free solidification constitute a prerequisite for the repair of real parts.
The rising of the temperature of the surrounding material through preheating constitute the most effective way to reduce the cooling rate and the cracking tendency. The preheating treatment generally used for gamma prime precipitation strengthened nickel base superalloys consists in heating the entire weld area to a ductile temperature set above the aging temperature (˜870° C.) and below the incipient melting temperature but might be defined as being set in between 950° C. and 1000° C. (U.S. Pat. No. 5,374,319).
Within this temperature range the thermal gradients are reduced by one or to order of magnitude and thus increase the risk for nucleation of spurious grains by increasing the driving force for nucleation. The process window for SX solidification is thus critically reduced which drastically limit the use of the SX laser assisted repair.
Such high preheating temperatures also constitute a risk for the process upscale to real parts as it can trigger recrystallization of location presenting high dislocation density (e.g. blade roots).
The limitation inherent to the use of the preheating treatment defined in the state of the art is solved trough the definition of a preheating treatment balancing those two conflicting features (spurious grain nucleation and hot cracking).
The optimal preheating temperature here proposed is below 500° C. This particular temperature allows reducing the yield strength of the surrounding material and thus the associated restraint which usually restrict the required shrinkage of the weld bead and lead to tensile stress build-up in the critical area while holding the driving force for spurious grain nucleation to a sufficiently low value.
The heating source employed may consist in an induction system allowing local heat treatment.
Taking into account the somewhat low temperature here defined the use of infrared lamp or defocused laser beam might be conceivable to achieve the desired preheating temperature.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows a gas turbine,

FIG. 2 shows a turbine blade,

FIG. 3 shows a combustion chamber,

FIG. 4, 5, 6 shows a component to be repaired by welding

FIG. 7 shows a listing of superalloys and

FIG. 8, 9 show experimental results.

DETAILED DESCRIPTION OF INVENTION

FIG. 1 shows, by way of example, a partial longitudinal section through a gas turbine 100. In the interior, the gas turbine 100 has a rotor 103 which is mounted such that it can rotate about an axis of rotation 102, has a shaft 101 and is also referred to as the turbine rotor.
An intake housing 104, a compressor 105, a, for example, toroidal combustion chamber 110, in particular an annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust-gas housing 109 follow one another along the rotor 103. The annular combustion chamber 110 is in communication with a, for example, annular hot-gas passage 111, where, by way of example, four successive turbine stages 112 form the turbine 108.
Each turbine stage 112 is formed, for example, from two blade or vane rings. As seen in the direction of flow of a working medium 113, in the hot-gas passage 111 a row of guide vanes 115 is followed by a row 125 formed from rotor blades 120.
The guide vanes 130 are secured to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are fitted to the rotor 103 for example by means of a turbine disk 133. A generator (not shown) is coupled to the rotor 103.
While the gas turbine 100 is operating, the compressor 105 sucks in air 135 through the intake housing 104 and compresses it. The compressed air provided at the turbine-side end of the compressor 105 is passed to the burners 107, where it is mixed with a fuel. The mix is then burnt in the combustion chamber 110, forming the working medium 113. From there, the working medium 113 flows along the hot-gas passage 111 past the guide vanes 130 and the rotor blades 120. The working medium 113 is expanded at the rotor blades 120, transferring its momentum, so that the rotor blades 120 drive the rotor 103 and the latter in turn drives the generator coupled to it.
While the gas turbine 100 is operating, the components which are exposed to the hot working medium 113 are subject to thermal stresses. The guide vanes 130 and rotor blades 120 of the first turbine stage 112, as seen in the direction of flow of the working medium 113, together with the heat shield bricks which line the annular combustion chamber 110, are subject to the highest thermal stresses.
To be able to withstand the temperatures which prevail there, they can be cooled by means of a coolant.
Substrates of the components may likewise have a directional structure, i.e. they are in single-crystal form (SX structure) or have only longitudinally oriented grains (DS structure).
By way of example, iron-based, nickel-based or cobalt-based superalloys are used as material for the components, in particular for the turbine blade or vane 120, 130 and components of the combustion chamber 110. Superalloys of this type are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
The guide vane 130 has a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 and a guide vane head at the opposite end from the guide vane root. The guide vane head faces the rotor 103 and is fixed to a securing ring 140 of the stator 143.
FIG. 2 shows a perspective view of a rotor blade 120 or guide vane 130 of a turbomachine, which extends along a longitudinal axis 121.
The turbomachine may be a gas turbine of an aircraft or of a power plant for generating electricity, a steam turbine or a compressor.
The blade or vane 120, 130 has, in succession along the longitudinal axis 121, a securing region 400, an adjoining blade or vane platform 403 and a main blade or vane part 406 as well as a blade or vane tip 415. As a guide vane 130, the vane 130 may have a further platform (not shown) at its vane tip 415.
A blade or vane root 183, which is used to secure the rotor blades 120, 130 to a shaft or disk (not shown), is formed in the securing region 400. The blade or vane root 183 is designed, for example, in hammerhead form. Other configurations, such as a fir-tree or dovetail root, are possible. The blade or vane 120, 130 has a leading edge 409 and a trailing edge 412 for a medium which flows past the main blade or vane part 406.
In the case of conventional blades or vanes 120, 130, by way of example solid metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade or vane 120, 130.
Superalloys of this type are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
The blade or vane 120, 130 may in this case be produced by a casting process, also by means of directional solidification, by a forging process, by a milling process or combinations thereof.
Workpieces with a single-crystal structure or structures are used as components for machines which, in operation, are exposed to high mechanical, thermal and/or chemical stresses. Single-crystal workpieces of this type are produced, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form the single-crystal structure, i.e. the single-crystal workpiece, or solidifies directionally.
In this case, dendritic crystals are oriented along the direction of heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and are referred to here, in accordance with the language customarily used, as directionally solidified) or a single-crystal structure, i.e. the entire workpiece consists of one single crystal. In these processes, a transition to globular (polycrystalline) solidification needs to be avoided, since non-directional growth inevitably forms transverse and longitudinal grain boundaries, which negate the favorable properties of the directionally solidified or single-crystal component.
Where the text refers in general terms to directionally solidified microstructures, this is to be understood as meaning both single crystals, which do not have any grain boundaries or at most have small-angle grain boundaries, and columnar crystal structures, which do have grain boundaries running in the longitudinal direction but do not have any transverse grain boundaries. This second form of crystalline structures is also described as directionally solidified microstructures (directionally solidified structures). Processes of this type are known from U.S. Pat. No. 6,024,792 and EP 0 892 090 A1.
The blades or vanes 120, 130 may likewise have coatings protecting against corrosion or oxidation, e.g. MCrAlX (M is at least one element selected from the group consisting of iron (Fe), cobalt (Co), nickel (Ni), X is an active element and represents yttrium (Y) and/or silicon and/or at least one rare earth element, or hafnium (Hf)). Alloys of this type are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1. The density is preferably 95% of the theoretical density. A protective aluminum oxide layer (TGO=thermally grown oxide layer) forms on the MCrAlX layer (as an intermediate layer or an outermost layer).
It is also possible for a thermal barrier coating, consisting for example of ZrO₂, Y₂O₃—ZrO₂, i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide, which is preferably the outermost layer, to be present on the MCrAlX.
The thermal barrier coating covers the entire MCrAlX layer. Columnar grains are produced in the thermal barrier coating by means of suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD).
Other coating processes are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD. The thermal barrier coating may include porous grains which have microcracks or macrocracks for improving its resistance to thermal shocks. The thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
The blade or vane 120, 130 may be hollow or solid in form. If the blade or vane 120, 130 is to be cooled, it is hollow and may also have film-cooling holes 418 (indicated by dashed lines).
FIG. 3 shows a combustion chamber 110 of the gas turbine 100. The combustion chamber 110 is configured, for example, as what is known as an annular combustion chamber, in which a multiplicity of burners 107 arranged circumferentially around an axis of rotation 102 open out into a common combustion chamber space 154 and generate flames 156. For this purpose, the combustion chamber 110 overall is of annular configuration positioned around the axis of rotation 102.
To achieve a relatively high efficiency, the combustion chamber 110 is designed for a relatively high temperature of the working medium M of approximately 1000° C. to 1600° C. To allow a relatively long service life even with these operating parameters, which are unfavorable for the materials, the combustion chamber wall 153 is provided, on its side which faces the working medium M, with an inner lining formed from heat shield elements 155.
A cooling system may also be provided for the heat shield elements 155 and/or their holding elements, on account of the high temperatures in the interior of the combustion chamber 110. The heat shield elements 155 are then, for example, hollow and if appropriate also have cooling holes (not shown) opening out into the combustion chamber space 154.
Each heat shield element 155 made from an alloy is provided on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and/or ceramic coating) or is made from high-temperature-resistant material (solid ceramic bricks).
These protective layers may be similar to those used for the turbine blades or vanes, i.e. for example meaning MCrAlX: M is at least one element selected from the group consisting of iron (Fe), cobalt (Co), nickel (Ni), X is an active element and represents yttrium (Y) and/or silicon and/or at least one rare earth element, or hafnium (Hf). Alloys of this type are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
It is also possible for a, for example, ceramic thermal barrier coating, consisting for example of ZrO₂, Y₂O₃—ZrO₂, i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide, to be present on the MCrAlX. Columnar grains are produced in the thermal barrier coating by means of suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD). Other coating processes are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD. The thermal barrier coating may have porous grains which have microcracks or macrocracks to improve its resistance to thermal shocks.
Refurbishment means that after they have been used, protective layers may have to be removed from turbine blades or vanes 120, 130, heat shield elements 155 (e.g. by sand-blasting). Then, the corrosion and/or oxidation layers and products are removed. If appropriate, cracks in the turbine blade or vane 120, 130 or the heat shield element 155 are also repaired. This is followed by recoating of the turbine blades or vanes 120, 130, heat shield elements 155, after which the turbine blades or vanes 120, 130 or the heat shield elements 155 can be reused.
FIG. 4 shows a component 1, 120, 130, 155, which comprises a substrate 4. The substrate 4 is especially made of a superalloy, especially of nickel base superalloy. Superalloys which can be repaired by this welding method are listed in FIG. 7, especially: PWA1483SX, CMSX4. This substrate 4 possesses a crack 10 or hole 10 which has to be closed. The hole 10 or crack 10 is a blind hole.
Especially the depth of the cracks 10 is between 0.75 mm up to 1.5 mm. Especially the depth of the cracks 10 is up to 1 mm, very especially in the range of 1 mm. The width of the crack 10 at the surface 22 of the substrate 4 is preferably in the range between 10 μm to 100 μm.
The preheating is preferably performed only locally around the area 10 to be welded and in the other regions the temperature is much lower.
Very good results have been obtained at temperatures <500° C., especially in a temperature range between 450° C. and 490° C., and very especially between 450° C. and 480° C.
“<500° C.” means that the measured preheating temperature is: T_preheat<500° C.−ΔT, wherein ΔT (>0) is the tolerance of measuring the temperature. A temperature >500° C. must strictly be avoided, because there is a strong increase in the occurrence of defect like cracks and/or grain misorientation of the resolidified melt (FIG. 9), wherein the number of defects is increased and yielding decreases (FIG. 9).
The preheating temperature is preferably maintained during welding.
Although there are several possibilities of lasers 13 as a welding device to be used it was found that a Nd—YAG or high power diode laser type is the best to be used. The diameter of the spot size of the laser beam is in the range of 2.5 mm to 5 mm, especially from 3 mm to 5 mm and very especially in the range of 4 mm. Surprisingly it was found that such a big diameter of the laser beam shows good results of repairing that small cracks 10, wherein, “small” relates to the crack width at the surface 22. The power P_Laser[W] of the laser 13 is between 450 Watt and 950 Watt, especially 500 Watt to 900 Watt, so that laser intensities of about 2.3 kw/cm²to 30 kw/cm², especially 2.5 kw/cm²to 29 kw/cm²are reached (FIG. 8). Otherwise the numbers of defects are increasing.
Preferably a relative movement of the laser beam and the substrate 4 to be repaired is ≦1 mm/s, especially A: ≦0.9 mm/s and very especially of 50 mm/min.
Preferably the relative movement is ≧0.4 mm/s, especially ≧0.6 mm/s.
Nevertheless, additional material 19 (FIG. 6), especially: PWA 1483, CMSX4 based powders can be added by a material feeder 16 (especially in form of powders) whose supplied material is melted again by the welding apparatus 13.

Claims

1.-22. (canceled)

23. A method of welding a component, comprising:

welding the component using a preheating temperature of the component below 500° C. and above 400° C.,

wherein no material is added to an area to be welded.

24. The method according to claim 23, wherein the preheating temperature is below 480° C.

25. The method according to claim 23, wherein the preheating temperature is above 450° C.

26. The method according to claim 23, wherein the component comprises a nickel based superalloy.

27. The method according to claim 23, wherein the component comprises a directionally solidified columnar grained superalloy.

28. The method according to claim 26, wherein the component comprises a single crystal super alloy.

29. The method according to claim 23, wherein a laser is used for the welding.

30. The method according to claim 24, wherein a plasma is used for the welding.

31. The method according to claim 23, wherein the component is preheated by an induction system.

32. The method according to claim 23, wherein the component is preheated by an infrared lamp.

33. The method according to claim 23, wherein the component is preheated by a laser especially also used for the welding.

34. The method according to claim 23, wherein the component is heated locally in the area to be welded.

35. The method according to claim 23, wherein the preheating temperature is maintained during the whole welding process.

36. The method according to claim 29, wherein a spot size of the laser has a diameter from 2.5 mm to 5 mm.

37. The method according to claim 29, wherein a power of the laser is between 500W and 900W.

38. The method according to claim 29, wherein a relative movement of the laser beam and the component is less than 1 mm/s.

39. The method according to claim 29, wherein a relative movement of the laser beam and the component is 1 mm/s.

40. The method according to claim 38, wherein the relative movement is 50 mm/min.

41. The method according to claim 29, wherein the laser is a Nd—YAG laser.

42. The method according to claim 23, wherein the welding method is a remelting process.